Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-s1010-il-50000 Airfoil,s1010-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,20.4409 Max Cl/Cd alpha,3.25 Url,http://www.airfoiltools.com/polar/csv?polar=xf-s1010-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.6435,0.11260,0.10562,0.0268,1.0000,0.2467 -9.000,-0.6664,0.11141,0.10458,0.0237,1.0000,0.2548 -8.750,-0.6523,0.10653,0.09967,0.0246,1.0000,0.2680 -8.500,-0.6401,0.10195,0.09508,0.0252,1.0000,0.2801 -8.250,-0.6413,0.09861,0.09181,0.0250,1.0000,0.2951 -8.000,-0.6460,0.09564,0.08892,0.0248,1.0000,0.3102 -7.750,-0.6299,0.09143,0.08468,0.0271,1.0000,0.3364 -7.500,-0.6283,0.08782,0.08113,0.0278,1.0000,0.3553 -7.250,-0.6164,0.08390,0.07719,0.0291,1.0000,0.3747 -6.750,-0.6751,0.05763,0.05013,-0.0106,1.0000,0.1420 -6.500,-0.6642,0.05253,0.04468,-0.0112,1.0000,0.1417 -6.250,-0.6513,0.04763,0.03927,-0.0114,1.0000,0.1422 -6.000,-0.6352,0.04291,0.03402,-0.0111,1.0000,0.1420 -5.750,-0.6172,0.03854,0.02894,-0.0104,1.0000,0.1438 -5.500,-0.5971,0.03583,0.02589,-0.0095,1.0000,0.1567 -5.250,-0.5752,0.03300,0.02284,-0.0085,1.0000,0.1688 -5.000,-0.5530,0.03054,0.01996,-0.0075,1.0000,0.1854 -4.750,-0.5295,0.02830,0.01761,-0.0065,1.0000,0.2032 -4.500,-0.5057,0.02646,0.01548,-0.0055,1.0000,0.2260 -4.250,-0.4810,0.02462,0.01363,-0.0046,1.0000,0.2483 -4.000,-0.4562,0.02304,0.01201,-0.0037,1.0000,0.2765 -3.750,-0.4304,0.02157,0.01050,-0.0028,1.0000,0.3112 -3.500,-0.4045,0.02012,0.00924,-0.0019,1.0000,0.3569 -3.250,-0.3802,0.01860,0.00809,-0.0007,1.0000,0.4240 -3.000,-0.2216,0.01642,0.00733,-0.0162,1.0000,1.0000 -2.750,-0.2042,0.01601,0.00661,-0.0153,1.0000,1.0000 -2.500,-0.1857,0.01570,0.00606,-0.0143,1.0000,1.0000 -2.250,-0.1668,0.01545,0.00560,-0.0132,1.0000,1.0000 -2.000,-0.1477,0.01525,0.00522,-0.0121,1.0000,1.0000 -1.750,-0.1287,0.01507,0.00487,-0.0108,1.0000,1.0000 -1.500,-0.1097,0.01493,0.00461,-0.0095,1.0000,1.0000 -1.250,-0.0909,0.01481,0.00439,-0.0080,1.0000,1.0000 -1.000,-0.0723,0.01472,0.00422,-0.0066,1.0000,1.0000 -0.750,-0.0539,0.01465,0.00409,-0.0050,1.0000,1.0000 -0.500,-0.0357,0.01460,0.00399,-0.0034,1.0000,1.0000 -0.250,-0.0178,0.01457,0.00393,-0.0017,1.0000,1.0000 0.000,0.0000,0.01456,0.00391,0.0000,1.0000,1.0000 0.250,0.0178,0.01457,0.00393,0.0017,1.0000,1.0000 0.500,0.0357,0.01460,0.00399,0.0034,1.0000,1.0000 0.750,0.0539,0.01465,0.00409,0.0050,1.0000,1.0000 1.000,0.0723,0.01472,0.00422,0.0066,1.0000,1.0000 1.250,0.0909,0.01481,0.00439,0.0080,1.0000,1.0000 1.500,0.1097,0.01493,0.00461,0.0095,1.0000,1.0000 1.750,0.1287,0.01507,0.00487,0.0108,1.0000,1.0000 2.000,0.1478,0.01525,0.00522,0.0121,1.0000,1.0000 2.250,0.1668,0.01545,0.00560,0.0132,1.0000,1.0000 2.500,0.1858,0.01570,0.00605,0.0143,1.0000,1.0000 2.750,0.2043,0.01600,0.00661,0.0153,1.0000,1.0000 3.000,0.2217,0.01641,0.00733,0.0161,1.0000,1.0000 3.250,0.3802,0.01860,0.00809,0.0007,0.4242,1.0000 3.500,0.4045,0.02012,0.00924,0.0019,0.3569,1.0000 3.750,0.4305,0.02157,0.01050,0.0028,0.3111,1.0000 4.000,0.4562,0.02304,0.01201,0.0036,0.2766,1.0000 4.250,0.4810,0.02463,0.01363,0.0046,0.2482,1.0000 4.500,0.5057,0.02646,0.01548,0.0055,0.2260,1.0000 4.750,0.5296,0.02830,0.01761,0.0065,0.2033,1.0000 5.000,0.5530,0.03053,0.01996,0.0075,0.1855,1.0000 5.250,0.5753,0.03300,0.02284,0.0085,0.1688,1.0000 5.500,0.5971,0.03582,0.02589,0.0095,0.1567,1.0000 5.750,0.6172,0.03853,0.02894,0.0104,0.1439,1.0000 6.000,0.6352,0.04291,0.03402,0.0111,0.1420,1.0000 6.250,0.6514,0.04762,0.03927,0.0114,0.1422,1.0000 6.500,0.6644,0.05253,0.04468,0.0112,0.1417,1.0000 6.750,0.6754,0.05763,0.05013,0.0106,0.1421,1.0000 7.000,0.6870,0.06475,0.05755,0.0091,0.1573,1.0000 7.250,0.6170,0.08391,0.07720,-0.0291,0.3744,1.0000 7.500,0.6320,0.08811,0.08143,-0.0277,0.3547,1.0000 7.750,0.6320,0.09159,0.08484,-0.0271,0.3369,1.0000 8.000,0.6477,0.09574,0.08901,-0.0249,0.3103,1.0000 8.250,0.6413,0.09860,0.09179,-0.0252,0.2950,1.0000 8.500,0.6410,0.10198,0.09512,-0.0253,0.2801,1.0000 8.750,0.6516,0.10645,0.09958,-0.0248,0.2678,1.0000 9.000,0.6670,0.11142,0.10458,-0.0238,0.2548,1.0000 9.250,0.6444,0.11265,0.10566,-0.0269,0.2464,1.0000